US7509873B2 - Method and apparatus for failure probability density function determination - Google Patents

Method and apparatus for failure probability density function determination Download PDF

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US7509873B2
US7509873B2 US11/615,921 US61592106A US7509873B2 US 7509873 B2 US7509873 B2 US 7509873B2 US 61592106 A US61592106 A US 61592106A US 7509873 B2 US7509873 B2 US 7509873B2
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distortion
shapes
fom
layups
layup
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Sharyn E. Mlinar
Matthew H. Cawthorne
David L. Downey
Donna M. Irby
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Boeing Co
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Boeing Co
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding

Definitions

  • This invention relates generally to the field of testing for failure criteria determination in composite matrices and more particularly to a protocol including a method for coupon fabrication and testing to determine failure characteristics in multi-ply composite systems with templates for distortion comparison and disposition.
  • Composite fabrication aircraft and helicopter structural systems requires high reliability for safety of flight elements. Testing for various voids or distortions in the plies of composite materials such as glass reinforced fiber composites and related determinations of engineering quality dispositions for anomalies that are located requires repeatable techniques for development of a database for use in such review. As an example, fiber distortions occur in helicopter rotor blade spar straps near critical root end stations. This area is critical because it is a force concentration area during the operation of the rotor blade. Any degradation of strength in that area is of concern.
  • the fiber distortion anomalies are detectable through various testing techniques such as X-ray.
  • the disposition can only be “use as is” or “scrap” depending on the severity of the distorted fibered composite. In the specific example this is particularly true if it occurs in the critical blade root end.
  • Current procedures have allowed a number of the blades to be dispositioned “use as is” following careful case-by-case evaluation.
  • the embodiments disclosed herein for the present invention provide a coupon fabrication technique with defined distortion in the form of marceled fibers and test protocol to determine the shape of the failure probability density curve to improve the analyses of the risk of fiber distortion anomalies in composite structures.
  • This protocol provides a method to determine the probability of and the severity of the various distorted fiber conditions that might exist on the rotor blades for the exemplary application in the future and those that are currently in fabrication and in service.
  • the response variable data and analyses information provided by the invention enables operations and quality personnel to make better informed decisions during production operations and at inspection points during the production and at final buy off of composite structural components using comparative standards derived from the distortion shapes employed in the coupon testing protocol.
  • the determination of the failure characteristics instigated by distorted fibers in the material also enables improvements to the design of future composite structures.
  • the data provided by the invention and associated finite element analyses which can be conducted based on the test protocol enhances engineering decision-making ability and add to the knowledge of composite materials engineering, stress engineering, quality engineering and composite testing and quality verifications.
  • FIG. 1 a is side view of a test coupon defined according to the protocol of the present invention
  • FIG. 1 b is a front view of the test coupon of FIG. 1 a;
  • FIG. 1 c is a front view of an exemplary test coupon with added gripping pads
  • FIG. 1 d is a side view of an exemplary test coupon with the added gripping pads.
  • FIG. 2 shows distortion curve shapes defined for selecting a test set according to the protocol of the invention and comparative standard templates for uncontoured regions;
  • FIG. 3 is a pictorial view of a resin pool distortion shape, as machined, during insertion into the layup;
  • FIGS. 4 a - 4 i show comparative standard templates for determination of distortion sizing
  • FIG. 5 shows comparative standard templates for pin regions with positive curvature
  • FIG. 6 shows comparative standard templates for pin regions with negative curvature.
  • the protocol of the present invention defines the impact of fiber distortion defects on the tensile strength property of composite lay-ups.
  • a coupon 100 shown in FIG. 1 c employs the same materials and simulates the wave-like characteristics found in marceled distortions present in production fiber composite layups.
  • For an exemplary composite system of BMS 08-196 Unidirectional coupons are built using a multi-ply layup incorporating a resign pool distortion shape selected from a distortion curve set as will be described in greater detail subsequently.
  • the layup comprises 40 layers.
  • the coupons are then sliced perpendicular to the layup with a thickness of approximately 0.050 inch. Tapes of varying width are created depending on the number of layers with 1.5 inch to 2.0 inch tapes 102 , shown in FIG.
  • sample coupons are prepared with the defect present in the surface layer, two layers from the surface and at the middle of the layers in the coupon.
  • a 40 ply layup is employed.
  • FIG. 2 shows exemplary curves 1 to 60 representative of half shapes for idealized cases of the marceled distortions found in composites studied.
  • Curves 1 - 10 have a height of 0.0625 inch with total length (cord) varying from 0.188 inch to 1.5 inches.
  • curves 11 - 20 have a height of 0.125 inch with cord varying from 0.188 to 1.5 inches.
  • Curves 21 - 30 have a height of 0.1875, curves 31 - 40 a height of 0.25 inch, curves 41 - 50 a height of 0.3125, curves 51 - 60 a height of 0.375 inch, curves 61 - 70 a height of 0.5 inch.
  • Selected ones of the curves as will be defined subsequently, have distortion shapes machined from resin pools comprised of the same resin as the composite under test.
  • a resin pool is cured and machined to provide a distortion shape 104 which is inserted between composite layup layers 108 at the location predetermined as previously described.
  • the middle layer location is shown in FIG. 3 as exemplary. Slicing of the layup to create the test coupons is accomplished as represented by line 1 a - 1 a.
  • a distortion category is created by establishing a figure of merit based on the amplitude of the distortion and its length.
  • the figure of merit is proportional to h 2 and L and is specifically defined by first determining the aspect ratio, h/L, based on the distortion amplitude and length for each of the shapes defined in FIG. 2 .
  • a determination of a figure of merit is then accomplished by multiplying the distortion amplitude by the aspect ratio multiplied by a percentage of fiber involvement. This function for the embodiment disclosed herein is equal to the percentage for lugs with less than 80% distortion and grows to 160% for completely involved lugs.
  • the testing protocol provides for the preparation of coupons as described previously with 2 category 2 curves, 2 category 3 and 2 category 4 to simulate the changes in both amplitude and wavelength that categorize a typical fiber distortion wave as a 2, 3, or 4.
  • the shape factor and the amplitude are controlled by the inserts that created by selecting a curve from the inspection standard that is a score of 2, 3, or 4. One that has a high (tall) amplitude and one that has a low (short) amplitude.
  • These 6 inserts provide the standard shapes for the resin pocket around which the fiber distortion is created. The location of the insert will either be at the edge, 2 plies in, or at the middle of the coupon, 20 plies in.
  • test protocol is repeated as required to determine initial failure using a load line parallel to or normal to the axis of the marcel with a force testing machine at varying head speeds. Repetition of the protocol for varying temperature and moisture or other operationally specific environmental conditions provides additional data to establish acceptance criteria.
  • the stress levels for fatigue testing will vary by material and category of distortion.
  • the data provided by the test protocol is then applied to the distortion characteristics defined in Table 2 to provide a definitive means for determining whether the associated defect as characterized by the table has engineering structural properties sufficient for a “use as is” determination or whether the structural properties warrant a “scrap” disposition.
  • the curves of FIG. 2 provide templates for determination of approximate shape of a distortion in a production composite identifiable using the tracer fibers present in the layup. Tracer fibers are doped prior to composite creation to allow visualization of fiber placement and distortion.
  • FIGS. 4 a - 4 i are employed in inspection to determine the number of plies affected by a distortion for the composite embodiments defined herein.
  • FIG. 4 a provides a boundary for a distortion involving 10 plies or less
  • FIG. 4 b a boundary for a distortion involving 20 plies or less
  • FIG. 4 c 30 plies or less
  • FIG. 4 d 40 plies or less
  • FIG. 4 e 50 plies or less
  • FIG. 4 g 70 plies or less FIG. 4 h 80 plies or less
  • FIGS. 5 and 6 provide templates for determination of approximate shape of a distortion in a production composite identifiable using the tracer fibers where the distortion is present in a region surrounding a pin in the layup.
  • FIG. 5 with shapes 1 A- 60 A provide the positive curvature while FIG. 6 with shapes 1 B- 60 B demonstrate a negative curvature.
  • the determined shape and number of plies involved in a distortion are then applied to define the distortion category for determining the appropriate disposition of the defect.

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  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

A coupon fabrication with defined distortion in the form of marceled fibers and test protocol is employed to determine the shape of the failure probability density curve to improve the analyses of the risk of fiber distortion anomalies in composite structures. This protocol provides a method to determine the probability of and the severity of the various distorted fiber conditions that might exist on composite structure in fabrication and in service. A distortion characterization matrix is established for determining test shapes and providing defect characterization based on the results of tests on the selected shapes. Coupons for test are created using resin pool.

Description

BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates generally to the field of testing for failure criteria determination in composite matrices and more particularly to a protocol including a method for coupon fabrication and testing to determine failure characteristics in multi-ply composite systems with templates for distortion comparison and disposition.
2. Description of the Related Art
Composite fabrication aircraft and helicopter structural systems requires high reliability for safety of flight elements. Testing for various voids or distortions in the plies of composite materials such as glass reinforced fiber composites and related determinations of engineering quality dispositions for anomalies that are located requires repeatable techniques for development of a database for use in such review. As an example, fiber distortions occur in helicopter rotor blade spar straps near critical root end stations. This area is critical because it is a force concentration area during the operation of the rotor blade. Any degradation of strength in that area is of concern.
The fiber distortion anomalies are detectable through various testing techniques such as X-ray. However, since no repair is possible upon detection of distorted fibers in the root end as in many other critical structural components in aircraft and helicopters, the disposition can only be “use as is” or “scrap” depending on the severity of the distorted fibered composite. In the specific example this is particularly true if it occurs in the critical blade root end. Current procedures have allowed a number of the blades to be dispositioned “use as is” following careful case-by-case evaluation.
Current fatigue and crack propagation models and statistical analysis methods employed in analyzing composite anomalies use the Miners Rule or the later fatigue model by Birnbaum-Saunders. Both are models for crack propagation in metal. No current models for glass reinforced composite materials are available. Some limited experimentation has been performed at the University of Akron, Cambridge University and numerous papers are available on the development of finite element models, for example Pratt, W. F. and Allen, M. S. Patterned Fiber Composites, Inc. Characterization and finite element model correlation of wavy composites; Caiazzo, A. and Orlet, M., McShane, H., Strait, L., and Rachau, C. The effects of marcel defects on composite structural properties. Little has been done in the development of empirical data for the determination of the shape of the failure curve for glass reinforced composite with marceled conditions.
It is therefore desirable to provide consistent and repeatable data for characterization of marceled conditions and their impact on the life of rotor blades and other crack-prone parts made from the same or similar material. Such information is desirable to catalog the physical properties for use in engineering disposition of comparable anomalies identified in production components and to validate the current inspection routines in the composite shop and also to calculate the risk to fielded rotorcraft and/or determine the impact on the manufacturing processes creating rotor blade root ends.
SUMMARY OF THE INVENTION
The embodiments disclosed herein for the present invention provide a coupon fabrication technique with defined distortion in the form of marceled fibers and test protocol to determine the shape of the failure probability density curve to improve the analyses of the risk of fiber distortion anomalies in composite structures. This protocol provides a method to determine the probability of and the severity of the various distorted fiber conditions that might exist on the rotor blades for the exemplary application in the future and those that are currently in fabrication and in service.
The response variable data and analyses information provided by the invention enables operations and quality personnel to make better informed decisions during production operations and at inspection points during the production and at final buy off of composite structural components using comparative standards derived from the distortion shapes employed in the coupon testing protocol.
The determination of the failure characteristics instigated by distorted fibers in the material also enables improvements to the design of future composite structures. The data provided by the invention and associated finite element analyses which can be conducted based on the test protocol enhances engineering decision-making ability and add to the knowledge of composite materials engineering, stress engineering, quality engineering and composite testing and quality verifications.
BRIEF DESCRIPTION OF THE DRAWINGS
These and other features and advantages of the present invention will be better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
FIG. 1 a is side view of a test coupon defined according to the protocol of the present invention;
FIG. 1 b is a front view of the test coupon of FIG. 1 a;
FIG. 1 c is a front view of an exemplary test coupon with added gripping pads;
FIG. 1 d is a side view of an exemplary test coupon with the added gripping pads.
FIG. 2 shows distortion curve shapes defined for selecting a test set according to the protocol of the invention and comparative standard templates for uncontoured regions;
FIG. 3 is a pictorial view of a resin pool distortion shape, as machined, during insertion into the layup;
FIGS. 4 a-4 i show comparative standard templates for determination of distortion sizing;
FIG. 5 shows comparative standard templates for pin regions with positive curvature; and,
FIG. 6 shows comparative standard templates for pin regions with negative curvature.
 DETAILED DESCRIPTION OF THE INVENTION
The protocol of the present invention defines the impact of fiber distortion defects on the tensile strength property of composite lay-ups. A coupon 100, shown in FIG. 1 c employs the same materials and simulates the wave-like characteristics found in marceled distortions present in production fiber composite layups. For an exemplary composite system of BMS 08-196 Unidirectional coupons are built using a multi-ply layup incorporating a resign pool distortion shape selected from a distortion curve set as will be described in greater detail subsequently. For example coupons described herein the layup comprises 40 layers. The coupons are then sliced perpendicular to the layup with a thickness of approximately 0.050 inch. Tapes of varying width are created depending on the number of layers with 1.5 inch to 2.0 inch tapes 102, shown in FIG. 1 a (exaggerated in the thickness dimension in the figure for clarity) and 1 b showing a 0.050 slice of the test element resin pool distortion shape 104 included at a predetermined position as described above. The cure cycle replicates the production cure for the material being tested. Gripping pads 106 are added at the top and bottom of the coupon for engagement in a tensile testing machine.
To replicate potential defect locations, sample coupons are prepared with the defect present in the surface layer, two layers from the surface and at the middle of the layers in the coupon. For the exemplary coupons discussed herein a 40 ply layup is employed.
FIG. 2 shows exemplary curves 1 to 60 representative of half shapes for idealized cases of the marceled distortions found in composites studied. Curves 1-10 have a height of 0.0625 inch with total length (cord) varying from 0.188 inch to 1.5 inches. Similarly, curves 11-20 have a height of 0.125 inch with cord varying from 0.188 to 1.5 inches. Curves 21-30 have a height of 0.1875, curves 31-40 a height of 0.25 inch, curves 41-50 a height of 0.3125, curves 51-60 a height of 0.375 inch, curves 61-70 a height of 0.5 inch. Selected ones of the curves, as will be defined subsequently, have distortion shapes machined from resin pools comprised of the same resin as the composite under test.
As shown in FIG. 3, a resin pool is cured and machined to provide a distortion shape 104 which is inserted between composite layup layers 108 at the location predetermined as previously described. The middle layer location is shown in FIG. 3 as exemplary. Slicing of the layup to create the test coupons is accomplished as represented by line 1 a-1 a.
A distortion category is created by establishing a figure of merit based on the amplitude of the distortion and its length. For the exemplary embodiment, the figure of merit is proportional to h2 and L and is specifically defined by first determining the aspect ratio, h/L, based on the distortion amplitude and length for each of the shapes defined in FIG. 2. A determination of a figure of merit is then accomplished by multiplying the distortion amplitude by the aspect ratio multiplied by a percentage of fiber involvement. This function for the embodiment disclosed herein is equal to the percentage for lugs with less than 80% distortion and grows to 160% for completely involved lugs. A defined distortion category is then determined based on the figure of merit by value assignment where if the figure of merit (FOM) is less than or equal to 0.125 then the distortion category is defined as 1. If 0.125<FOM<=0.25 the distortion category is defined as 1.5. If 0.25<FOM<=0.85 the distortion category is defined as 2. If 0.85<FOM<=1.75 the distortion category is defined as 2.5. If 1.75<FOM<=3.1 the distortion category is defined as 3. If 3.1<FOM<=4.8 the distortion category is defined as 3.5. If 4.8<FOM<=6.8 the distortion category is defined as 4. If 6.8<FOM<=9.3 the distortion category is 4.5. While if the FOM>9.3 the distortion category is defined as 5. Table 1 shows the resulting aspect ratio and calculated FOM for the distortion shapes of FIG. 2. Table 2 provides the resulting distortion category with values over 5 being ignored.
TABLE 1
% % % % % % % % % %
h L 0.100 0.200 0.300 0.400 0.500 0.600 0.700 0.800 1.100 1.600 h/L
0.063 0.188 0.208 0.417 0.625 0.833 1.042 1.250 1.458 1.667 2.292 3.333 3.0
0.063 0.25 0.156 0.313 0.469 0.625 0.781 0.938 1.094 1.250 1.719 2.500 4.0
0.063 0.375 0.104 0.208 0.313 0.417 0.521 0.625 0.729 0.833 1.146 1.667 6.0
0.063 0.5 0.078 0.156 0.234 0.313 0.391 0.469 0.547 0.625 0.859 1.250 8.0
0.063 0.625 0.063 0.125 0.188 0.250 0.313 0.375 0.438 0.500 0.688 1.000 10.0
0.063 0.75 0.052 0.104 0.156 0.208 0.260 0.313 0.365 0.417 0.573 0.833 12.0
0.063 0.875 0.045 0.089 0.134 0.179 0.223 0.268 0.313 0.357 0.491 0.714 14.0
0.063 1 0.039 0.078 0.117 0.156 0.195 0.234 0.273 0.313 0.430 0.625 16.0
0.063 1.25 0.031 0.063 0.094 0.125 0.156 0.188 0.219 0.250 0.344 0.500 20.0
0.063 1.5 0.026 0.052 0.078 0.104 0.130 0.156 0.182 0.208 0.286 0.417 24.0
0.125 0.188 0.833 1.667 2.500 3.333 4.167 5.000 5.833 6.667 9.167 13.333 1.5
0.125 0.25 0.625 1.250 1.875 2.500 3.125 3.750 4.375 5.000 6.875 10.000 2.0
0.125 0.375 0.417 0.833 1.250 1.667 2.083 2.500 2.917 3.333 4.583 6.667 3.0
0.125 0.5 0.313 0.625 0.938 1.250 1.563 1.875 2.188 2.500 3.438 5.000 4.0
0.125 0.625 0.250 0.500 0.750 1.000 1.250 1.500 1.750 2.000 2.750 4.000 5.0
0.125 0.75 0.208 0.417 0.625 0.833 1.042 1.250 1.458 1.667 2.292 3.333 6.0
0.125 0.875 0.179 0.357 0.536 0.714 0.893 1.071 1.250 1.429 1.964 2.857 7.0
0.125 1 0.156 0.313 0.469 0.625 0.781 0.938 1.094 1.250 1.719 2.500 8.0
0.125 1.25 0.125 0.250 0.375 0.500 0.625 0.750 0.875 1.000 1.375 2.000 10.0
0.125 1.5 0.104 0.208 0.313 0.417 0.521 0.625 0.729 0.833 1.146 1.667 12.0
0.188 0.188 1.875 3.750 5.625 7.500 9.375 11.250 13.125 15.000 20.625 30.000 1.0
0.188 0.25 1.406 2.813 4.219 5.625 7.031 8.438 9.844 11.250 15.469 22.500 1.3
0.188 0.375 0.938 1.875 2.813 3.750 4.688 5.625 6.563 7.500 10.313 15.000 2.0
0.188 0.5 0.703 1.406 2.109 2.813 3.516 4.219 4.922 5.625 7.734 11.250 2.7
0.188 0.625 0.563 1.125 1.688 2.250 2.813 3.375 3.938 4.500 6.188 9.000 3.3
0.188 0.75 0.469 0.938 1.406 1.875 2.344 2.813 3.281 3.750 5.156 7.500 4.0
0.188 0.875 0.402 0.804 1.205 1.607 2.009 2.411 2.813 3.214 4.420 6.429 4.7
0.188 1 0.352 0.703 1.055 1.406 1.758 2.109 2.461 2.813 3.867 5.625 5.3
0.188 1.25 0.281 0.563 0.844 1.125 1.406 1.688 1.969 2.250 3.094 4.500 6.7
0.188 1.5 0.234 0.469 0.703 0.938 1.172 1.406 1.641 1.875 2.578 3.750 8.0
0.25 0.1875 3.333 6.667 10.000 13.333 16.667 20.000 23.333 26.667 36.667 53.333 0.8
0.25 0.25 2.500 5.000 7.500 10.000 12.500 15.000 17.500 20.000 27.500 40.000 1.0
0.25 0.375 1.667 3.333 5.000 6.667 8.333 10.000 11.667 13.333 18.333 26.667 1.5
0.25 0.5 1.250 2.500 3.750 5.000 6.250 7.500 8.750 10.000 13.750 20.000 2.0
0.25 0.625 1.000 2.000 3.000 4.000 5.000 6.000 7.000 8.000 11.000 16.000 2.5
0.25 0.75 0.833 1.667 2.500 3.333 4.167 5.000 5.833 6.667 9.167 13.333 3.0
0.25 0.875 0.714 1.429 2.143 2.857 3.571 4.286 5.000 5.714 7.857 11.429 3.5
0.25 1 0.625 1.250 1.875 2.500 3.125 3.750 4.375 5.000 6.875 10.000 4.0
0.25 1.25 0.500 1.000 1.500 2.000 2.500 3.000 3.500 4.000 5.500 8.000 5.0
0.25 1.5 0.417 0.833 1.250 1.667 2.083 2.500 2.917 3.333 4.583 6.667 6.0
0.3125 0.1875 5.208 10.417 15.625 20.833 26.042 31.250 36.458 41.667 57.292 83.333 0.6
0.3125 0.25 3.906 7.813 11.719 15.625 19.531 23.438 27.344 31.250 42.969 62.500 0.8
0.3125 0.375 2.604 5.208 7.813 10.417 13.021 15.625 18.229 20.833 28.646 41.667 1.2
0.3125 0.5 1.953 3.906 5.859 7.813 9.766 11.719 13.672 15.625 21.484 31.250 1.6
0.3125 0.625 1.563 3.125 4.688 6.250 7.813 9.375 10.938 12.500 17.188 25.000 2.0
0.3125 0.75 1.302 2.604 3.906 5.208 6.510 7.813 9.115 10.417 14.323 20.833 2.4
0.3125 0.875 1.116 2.232 3.348 4.464 5.580 6.696 7.813 8.929 12.277 17.857 2.8
0.3125 1 0.977 1.953 2.930 3.906 4.883 5.859 6.836 7.813 10.742 15.625 3.2
0.3125 1.25 0.781 1.563 2.344 3.125 3.906 4.688 5.469 6.250 8.594 12.500 4.0
0.3125 1.5 0.651 1.302 1.953 2.604 3.255 3.906 4.557 5.208 7.161 10.417 4.8
0.375 0.1875 7.500 15.000 22.500 30.000 37.500 45.000 52.500 60.000 82.500 120.000 0.5
0.375 0.25 5.625 11.250 16.875 22.500 28.125 33.750 39.375 45.000 61.875 90.000 0.7
0.375 0.375 3.750 7.500 11.250 15.000 18.750 22.500 26.250 30.000 41.250 60.000 1.0
0.375 0.5 2.813 5.625 8.438 11.250 14.063 16.875 19.688 22.500 30.938 45.000 1.3
0.375 0.625 2.250 4.500 6.750 9.000 11.250 13.500 15.750 18.000 24.750 36.000 1.7
0.375 0.75 1.875 3.750 5.625 7.500 9.375 11.250 13.125 15.000 20.625 30.000 2.0
0.375 0.875 1.607 3.214 4.821 6.429 8.036 9.643 11.250 12.857 17.679 25.714 2.3
0.375 1 1.406 2.813 4.219 5.625 7.031 8.438 9.844 11.250 15.469 22.500 2.7
0.375 1.25 1.125 2.250 3.375 4.500 5.625 6.750 7.875 9.000 12.375 18.000 3.3
0.375 1.5 0.938 1.875 2.813 3.750 4.688 5.625 6.563 7.500 10.313 15.000 4.0
0.5 0.1875 13.333 26.667 40.000 53.333 66.667 80.000 93.333 106.667 146.667 213.333 0.4
0.5 0.25 10.000 20.000 30.000 40.000 50.000 60.000 70.000 80.000 110.000 160.000 0.5
0.5 0.375 6.667 13.333 20.000 26.667 33.333 40.000 46.667 53.333 73.333 106.667 0.8
0.5 0.5 5.000 10.000 15.000 20.000 25.000 30.000 35.000 40.000 55.000 80.000 1.0
0.5 0.625 4.000 8.000 12.000 16.000 20.000 24.000 28.000 32.000 44.000 64.000 1.3
0.5 0.75 3.333 6.667 10.000 13.333 16.667 20.000 23.333 26.667 36.667 53.333 1.5
0.5 0.875 2.857 5.714 8.571 11.429 14.286 17.143 20.000 22.857 31.429 45.714 1.8
0.5 1 2.500 5.000 7.500 10.000 12.500 15.000 17.500 20.000 27.500 40.000 2.0
0.5 1.25 2.000 4.000 6.000 8.000 10.000 12.000 14.000 16.000 22.000 32.000 2.5
0.5 1.5 1.667 3.333 5.000 6.667 8.333 10.000 11.667 13.333 18.333 26.667 3.0
TABLE 2
% % % % % % % % % %
h L 10% 20% 30% 40% 50% 60% 70% 80% 90% 100%
1 0.063 0.188 1.5 2.0 2.0 2.0 2.5 2.5 2.5 2.5 3.0 3.5
2 0.063 0.25 1.5 2.0 2.0 2.0 2.0 2.5 2.5 2.5 2.5 3.0
3 0.063 0.375 1.0 1.5 2.0 2.0 2.0 2.0 2.0 2.0 2.5 2.5
4 0.063 0.5 1.0 1.5 1.5 2.0 2.0 2.0 2.0 2.0 2.5 2.5
5 0.063 0.625 1.0 1.5 1.5 2.0 2.0 2.0 2.0 2.0 2.0 2.5
6 0.063 0.75 1.0 1.0 1.5 1.5 2.0 2.0 2.0 2.0 2.0 2.0
7 0.063 0.875 1.0 1.0 1.5 1.5 1.5 2.0 2.0 2.0 2.0 2.0
8 0.063 1 1.0 1.0 1.0 1.5 1.5 1.5 2.0 2.0 2.0 2.0
9 0.063 1.25 1.0 1.0 1.0 1.5 1.5 1.5 1.5 2.0 2.0 2.0
10 0.063 1.5 1.0 1.0 1.0 1.0 1.5 1.5 1.5 1.5 2.0 2.0
11 0.125 0.188 2.0 2.5 3.0 3.5 3.5 4.0 4.0 4.0 4.5 5.0
12 0.125 0.25 2.0 2.5 3.0 3.0 3.5 3.5 3.5 4.0 4.5 5.0
13 0.125 0.375 2.0 2.0 2.5 2.5 3.0 3.0 3.0 3.5 3.5 4.0
14 0.125 0.5 2.0 2.0 2.5 2.5 2.5 3.0 3.0 3.0 3.5 4.0
15 0.125 0.625 2.0 2.0 2.0 2.5 2.5 2.5 3.0 3.0 3.0 3.5
16 0.125 0.75 1.5 2.0 2.0 2.0 2.5 2.5 2.5 2.5 3.0 3.5
17 0.125 0.875 1.5 2.0 2.0 2.0 2.5 2.5 2.5 2.5 3.0 3.0
18 0.125 1 1.5 2.0 2.0 2.0 2.0 2.5 2.5 2.5 2.5 3.0
19 0.125 1.25 1.5 2.0 2.0 2.0 2.0 2.0 2.5 2.5 2.5 3.0
20 0.125 1.5 1.0 1.5 2.0 2.0 2.0 2.0 2.0 2.0 2.5 2.5
21 0.188 0.188 3.0 3.5 4.0 4.5 5.0 5.0
22 0.188 0.25 2.5 3.0 3.5 4.0 4.5 4.5 5.0 5.0
23 0.188 0.375 2.5 3.0 3.0 3.5 3.5 4.0 4.0 4.5 5.0 5.0
24 0.188 0.5 2.0 2.5 3.0 3.0 3.5 3.5 4.0 4.0 4.5 5.0
25 0.188 0.625 2.0 2.5 2.5 3.0 3.0 3.5 3.5 3.5 4.0 4.5
26 0.188 0.75 2.0 2.5 2.5 3.0 3.0 3.0 3.5 3.5 4.0 4.5
27 0.188 0.875 2.0 2.0 2.5 2.5 3.0 3.0 3.0 3.5 3.5 4.0
28 0.188 1 2.0 2.0 2.5 2.5 3.0 3.0 3.0 3.0 3.5 4.0
29 0.188 1.25 2.0 2.0 2.0 2.5 2.5 2.5 3.0 3.0 3.0 3.5
30 0.188 1.5 1.5 2.0 2.0 2.5 2.5 2.5 2.5 3.0 3.0 3.5
31 0.25 0.188 3.5 4.0 5.0 5.0
32 0.25 0.25 3.0 4.0 4.5 5.0 5.0
33 0.25 0.375 2.5 3.5 4.0 4.0 4.5 5.0 5.0
34 0.25 0.5 2.5 3.0 3.5 4.0 4.0 4.5 4.5 5.0 5.0
35 0.25 0.625 2.5 3.0 3.0 3.5 4.0 4.0 4.5 4.5 5.0 5.0
36 0.25 0.75 2.0 2.5 3.0 3.5 3.5 4.0 4.0 4.0 4.5 5.0
37 0.25 0.875 2.0 2.5 3.0 3.0 3.5 3.5 4.0 4.0 4.5 5.0
38 0.25 1 2.0 2.5 3.0 3.0 3.5 3.5 3.5 4.0 4.5 5.0
39 0.25 1.25 2.0 2.5 2.5 3.0 3.0 3.0 3.5 3.5 4.0 4.5
40 0.25 1.5 2.0 2.0 2.5 2.5 3.0 3.0 3.0 3.5 3.5 4.0
41 0.313 0.188 4.0 5.0
42 0.313 0.25 3.5 4.5 5.0 5.0
43 0.313 0.375 3.0 4.0 4.5 5.0 5.0
44 0.313 0.5 3.0 3.5 4.0 4.5 5.0 5.0
45 0.313 0.625 2.5 3.5 3.5 4.0 4.5 5.0 5.0
46 0.313 0.75 2.5 3.0 3.5 4.0 4.0 4.5 4.5 5.0 5.0
47 0.313 0.875 2.5 3.0 3.5 3.5 4.0 4.0 4.5 4.5 5.0 5.0
48 0.313 1 2.5 3.0 3.0 3.5 4.0 4.0 4.5 4.5 5.0 5.0
49 0.313 1.25 2.0 2.5 3.0 3.5 3.5 3.5 4.0 4.0 4.5 5.0
50 0.313 1.5 2.0 2.5 3.0 3.0 3.5 3.5 3.5 4.0 4.5 5.0
51 0.375 0.188 4.5 5.0
52 0.375 0.25 4.0 5.0 5.0
53 0.375 0.375 3.5 4.5 5.0 5.0
54 0.375 0.5 3.0 4.0 4.5 5.0 5.0
55 0.375 0.625 3.0 3.5 4.0 4.5 5.0 5.0
56 0.375 0.75 3.0 3.5 4.0 4.5 5.0 5.0
57 0.375 0.875 2.5 3.5 4.0 4.0 4.5 5.0 5.0
58 0.375 1 2.5 3.0 3.5 4.0 4.5 4.5 5.0 5.0
59 0.375 1.25 2.5 3.0 3.5 3.5 4.0 4.0 4.5 4.5 5.0 5.0
60 0.375 1.5 2.5 3.0 3.0 3.5 3.5 4.0 4.0 4.5 5.0 5.0
61 0.500 0.188 5.0
62 0.500 0.25 5.0
63 0.500 0.375 4.0 5.0
64 0.500 0.5 4.0 5.0
65 0.500 0.625 3.5 4.5 5.0
66 0.500 0.75 3.5 4.0 5.0 5.0
67 0.500 0.875 3.0 4.0 4.5 5.0 5.0
68 0.500 1 3.0 4.0 4.5 5.0 5.0
69 0.500 1.25 3.0 3.5 4.0 4.5 5.0 5.0
70 0.500 1.5 2.5 3.5 4.0 4.0 4.5 5.0 5.0
The testing protocol provides for the preparation of coupons as described previously with 2 category 2 curves, 2 category 3 and 2 category 4 to simulate the changes in both amplitude and wavelength that categorize a typical fiber distortion wave as a 2, 3, or 4. The shape factor and the amplitude are controlled by the inserts that created by selecting a curve from the inspection standard that is a score of 2, 3, or 4. One that has a high (tall) amplitude and one that has a low (short) amplitude. These 6 inserts provide the standard shapes for the resin pocket around which the fiber distortion is created. The location of the insert will either be at the edge, 2 plies in, or at the middle of the coupon, 20 plies in.
The resulting test design is shown in Table 3
TABLE 3
Wave
StdOrder RunOrder Amplitude Shape location
17 1 short 3 edge
14 2 short 1 middle
3 3 short 2 edge
18 4 short 3 middle
12 5 tall 3 middle
22 6 tall 2 middle
34 7 tall 2 middle
13 8 short 1 edge
9 9 tall 2 edge
35 10 tall 3 edge
6 11 short 3 middle
19 12 tall 1 edge
26 13 short 1 middle
29 14 short 3 edge
27 15 short 2 edge
16 16 short 2 middle
24 17 tall 3 middle
15 18 short 2 edge
30 19 short 3 middle
36 20 tall 3 middle
7 21 tall 1 edge
25 22 short 1 edge
5 23 short 3 edge
1 24 short 1 edge
2 25 short 1 middle
33 26 tall 2 edge
23 27 tall 3 edge
4 28 short 2 middle
32 29 tall 1 middle
20 30 tall 1 middle
31 31 tall 1 edge
21 32 tall 2 edge
10 33 tall 2 middle
11 34 tall 3 edge
8 35 tall 1 middle
28 36 short 2 middle
The test protocol is repeated as required to determine initial failure using a load line parallel to or normal to the axis of the marcel with a force testing machine at varying head speeds. Repetition of the protocol for varying temperature and moisture or other operationally specific environmental conditions provides additional data to establish acceptance criteria. The stress levels for fatigue testing will vary by material and category of distortion.
The data provided by the test protocol is then applied to the distortion characteristics defined in Table 2 to provide a definitive means for determining whether the associated defect as characterized by the table has engineering structural properties sufficient for a “use as is” determination or whether the structural properties warrant a “scrap” disposition.
The curves of FIG. 2 provide templates for determination of approximate shape of a distortion in a production composite identifiable using the tracer fibers present in the layup. Tracer fibers are doped prior to composite creation to allow visualization of fiber placement and distortion.
The templates of FIGS. 4 a-4 i are employed in inspection to determine the number of plies affected by a distortion for the composite embodiments defined herein. FIG. 4 a provides a boundary for a distortion involving 10 plies or less, FIG. 4 b a boundary for a distortion involving 20 plies or less FIG. 4 c 30 plies or less, FIG. 4 d 40 plies or less, FIG. 4 e 50 plies or less, FIG. 4 f 60 plies or less, FIG. 4 g 70 plies or less, FIG. 4 h 80 plies or less and FIG. 4 i 90 plies or less.
FIGS. 5 and 6 provide templates for determination of approximate shape of a distortion in a production composite identifiable using the tracer fibers where the distortion is present in a region surrounding a pin in the layup. FIG. 5 with shapes 1A-60A provide the positive curvature while FIG. 6 with shapes 1B-60B demonstrate a negative curvature.
The determined shape and number of plies involved in a distortion are then applied to define the distortion category for determining the appropriate disposition of the defect.
Having now described the invention in detail as required by the patent statutes, those skilled in the art will recognize modifications and substitutions to the specific embodiments disclosed herein. Such modifications are within the scope and intent of the present invention as defined in the following claims.

Claims (10)

1. A method for testing marceled defects in composite materials comprising the steps of:
defining a distortion category matrix based on shape of a distortion,
preparing a plurality of predetermined distortion shapes precured from base resin;
inserting each of the plurality of distortion shapes in a predetermined position in a composite layup;
creating a plurality of multiple ply layups, each layup including one of the distortion shapes;
curing the multiple ply layups;
slicing each of the layups perpendicular to the layup direction to create coupons for testing;
fatigue testing each of the plurality of multiple ply layups.
2. A method as defined in claim 1 wherein the step of creating a plurality of multiple ply layups includes placing the distortion shape at a surface ply.
3. A method as defined in claim 1 wherein the step of creating a plurality of multiple ply layups includes placing the distortion shape 2 layers in from the surface ply.
4. A method as defined in claim 1 wherein the step of creating a plurality of multiple ply layups includes placing the distortion shape at the center of the layup.
5. A method as defined in claim 1 wherein the step of preparing a plurality of predetermined distortion shapes includes
machining a distortion shape in a mold;
filling the mold with resin; and
precuring the resin pool distortion shape.
6. A method as defined in claim 1 further comprising the steps of
creating a fatigue life determination matrix for each resin pool distortion shape and location
establishing a disposition criterion based on the fatigue life determination matrix.
7. A method for testing marceled defects in composite materials comprising the steps of:
defining a matrix of distortion shapes;
determining the aspect ratio, h/L, based on the distortion amplitude and length for each of the shapes;
determining a figure of merit based on the aspect ratio relative to overall fiber distortion; and,
establishing a distortion category based on the figure of merit;
preparing a plurality of predetermined distortion shapes from base resin;
inserting each of the plurality of distortion shapes in a predetermined position in a composite layup;
creating a plurality of multiple ply layups, each layup including one of the distortion shapes;
curing the multiple ply layups;
slicing each of the layups perpendicular to the layup direction to create coupons for testing;
fatigue testing each of the plurality of multiple ply layups.
8. A method as defined in claim 7 wherein the predetermined distortion shapes are defined by selection of chosen distortion categories and a set of associated amplitudes.
9. A method as defined in claim 7 wherein the step of determining a figure of merit comprises the step of multiplying the distortion length by the aspect ratio multiplied by a percentage of fiber involvement based on a function equal to said percentage for lugs with less than 80% distortion and growing to 160% for completely involved lugs.
10. A method as defined in claim 9 wherein the step of establishing a distortion category comprises the step of defining the distortion category as 1 if the FOM is less than or equal to 0.125; 1.5 if 0.125<FOM<=0.25; 2 if 0.25<FOM<=0.85; 2.5 if 0.85<FOM<=1.75; 3 if 1.75<FOM<=3.1; 3.5 if 3.1<FOM<=4.8; 4 if 4.8<FOM<=6.8; 4.5 if 6.8<FOM<=9.3; and 5 if the FOM>9.
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